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WO2017048041A1 - Moteur-fusée à propergol liquide s'appuyant sur une pompe de suralimentation entraînée par un moteur électrique - Google Patents

Moteur-fusée à propergol liquide s'appuyant sur une pompe de suralimentation entraînée par un moteur électrique Download PDF

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Publication number
WO2017048041A1
WO2017048041A1 PCT/KR2016/010319 KR2016010319W WO2017048041A1 WO 2017048041 A1 WO2017048041 A1 WO 2017048041A1 KR 2016010319 W KR2016010319 W KR 2016010319W WO 2017048041 A1 WO2017048041 A1 WO 2017048041A1
Authority
WO
WIPO (PCT)
Prior art keywords
oxidant
fuel
electric motor
booster pump
pump
Prior art date
Application number
PCT/KR2016/010319
Other languages
English (en)
Korean (ko)
Inventor
곽현덕
김진한
김대진
최창호
Original Assignee
한국항공우주연구원
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 한국항공우주연구원 filed Critical 한국항공우주연구원
Priority to KR1020187010421A priority Critical patent/KR102041568B1/ko
Priority to EP16846862.7A priority patent/EP3318745B1/fr
Priority to US15/750,757 priority patent/US11060482B2/en
Publication of WO2017048041A1 publication Critical patent/WO2017048041A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K5/00—Casings; Enclosures; Supports
    • H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
    • H02K5/20—Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
    • H02K5/203—Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium specially adapted for liquids, e.g. cooling jackets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Definitions

  • the present invention relates to a liquid rocket engine using a booster pump driven by an electric motor, and more particularly, by installing a booster pump between a propellant tank and a propellant pump, even if the internal pressure of the propellant tank is lowered. It can meet the inlet pressure to reduce the weight of the propellant tank, and the liquid rocket using the booster pump driven by the electric motor that can efficiently cool the electric motor driving the booster pump through the propellant and the cooling line. It's about the engine.
  • a turbopump engine for a rocket using a liquid propellant is to generate a thrust by sending the oxidant and fuel to the main combustion engine at a high pressure by using the hot gas generated in the gas generator.
  • a rocket turbopump engine using such a liquid propellant has a main combustion unit 11 for burning an oxidant and fuel, and a main oxidant line 12 guiding the oxidant to the main combustion unit 11.
  • Auxiliary fuel line 16 for guiding a portion of the fuel to gas generator 14, turbine 17 rotated by the high temperature and high pressure gas of gas generator 14, and oxidant pump interlocked monoaxially with turbine 17. 18 and a fuel pump 19.
  • the main oxidant on-off valve 12a and the main combustion machine 11 which turn on and off the oxidant guided to the main combustion machine 11.
  • the auxiliary fuel opening / closing valve 16a for turning off and reference numeral 17a are gas discharge pipes 17a for discharging gas passing through the turbine 17 to the outside.
  • Unexplained reference numeral 21 denotes a correction valve or orifice for correcting a thrust error
  • reference numeral 22 denotes a pyro starter or a turbine starter.
  • the starting process of the rocket turbopump engine using the liquid propellant is as follows.
  • the turbine 17 is first driven by the turbine starter 22 to create a state in which the pressure is increased by the oxidant pump 18 and the fuel pump 19.
  • the auxiliary oxidant valve 15a and the auxiliary fuel valve 16a are opened to supply the oxidant and fuel (hereinafter referred to as "propellant") to the gas generator 14.
  • the supplied propellant burns in the gas generator 14 to generate combustion gas, and the hot combustion gas drives the turbine 17 again to supply the oxidant pump 18 and the fuel pump 19 (hereinafter referred to as oxidant pump and fuel pump).
  • oxidant pump and fuel pump Collectively referred to as "pump").
  • main valve 12a and the main fuel valve 13a (hereinafter, the main oxidant valve and the main fuel valve) when the gas generator 14 is driven to generate a certain pressure of the pumps 18 and 19.
  • main valve is opened to supply propellant to the main combustion chamber (11).
  • the propellant supplied is burned in the main combustion machine 11 and discharged to the outside through the nozzle as a hot gas. This process starts the engine.
  • the propellant supplied to the oxidant pump and the fuel pump inlet must be maintained at a certain level or more to suppress the cavitation occurring in each pump.
  • the fuel tank must be maintained at a certain level of internal pressure and designed to be above a certain thickness to withstand the internal pressure. Therefore, there is a problem that the weight of the propellant tank increases in the projectile.
  • Korean Patent No. 10-0654412 includes a combustion chamber 110 as shown in FIG. 5; A fuel supply pump 120 for supplying fuel to the combustion chamber; An oxidant supply pump 130 for supplying an oxidant to the combustion chamber; A gas generator 140 receiving a portion of the fuel and the oxidant supplied from the fuel supply unit and the oxidant supply unit to generate a gas; A turbine 150 which rotates by receiving the gas generated from the gas generator and drives the fuel supply pump and the oxidant supply pump; A thrust control valve 160 for controlling the amount of oxidant supplied to the gas generator; An oxidant bypass pipe (170) branched from the gas generator side of the thrust control valve; And a mixing ratio stabilizer 200 for controlling the fuel supplied to the gas generating unit in accordance with the oxidant pressure supplied to the oxidant bypass pipe, from the fuel booster pump 126 and the oxidant booster pump 136 in which the oxidant is stored.
  • a liquid propellant rocket engine 100 configured to flow each liquid.
  • booster pumps are driven by a hydraulic turbine, which bypasses some of the high-pressure propellant at each propellant pump outlet to run the hydraulic turbine, which complicates the system and results in additional pump efficiency loss. There is a problem that occurs.
  • an object of the present invention is to provide a booster pump driven by an electric motor, to provide a liquid rocket engine for cooling the electric motor using a propellant.
  • a specific purpose of the present invention is to install a booster pump between the propellant tank and the propellant pump, it is possible to meet the inlet pressure required by the propellant pump even when the internal pressure of the propellant tank is lowered to reduce the weight of the propellant tank.
  • a liquid rocket engine using a booster pump driven by an electric motor includes a main combustion unit configured to combust an oxidant and fuel, and guide the oxidant contained in an oxidant tank to the main combustion unit.
  • a main oxidant line a main fuel line for guiding the fuel contained in a fuel tank to the main combustor, an oxidant pump disposed in the main oxidant line, a fuel pump disposed in the main fuel line, the oxidant tank and the An oxidant booster pump installed in the main oxidant line between the oxidant pump, a fuel booster pump installed in the main fuel line between the fuel tank and the fuel pump, and spaced between the oxidant booster pump and the fuel booster pump Disposed, the oxidant booster pump and the fuel booster An electric motor for driving a pump and branched at one side of the main oxidant line to guide a portion of the oxidant to the electric motor, or branched at one side of the main fuel line to cool a portion of the fuel to the electric motor A line, a cooling unit connected to the cooling line and installed in the electric motor, and a condenser installed in the cooling line, wherein at least one of the oxidant and the fuel moves the cooling line to cool the electric motor. It provides a liquid
  • the liquid rocket engine using the booster pump driven by the electric motor according to the present invention having the above configuration has the effect of installing the booster pump driven by the electric motor and cooling the electric motor by using a propellant.
  • liquid rocket engine using the booster pump driven by the electric motor by installing a booster pump between the propellant tank and the propellant pump, even if the internal pressure of the propellant tank is lowered, the inlet pressure required by the propellant pump The weight of the propellant tank can be reduced, and the electric motor driving the booster pump can be efficiently cooled through an oxidant and a cooling line.
  • FIGS. 1A and 1B are conceptual views illustrating a structure of a liquid rocket engine using a booster pump driven by an electric motor according to an embodiment of the present invention and a modification thereof.
  • FIGS. 1C to 1E are conceptual views illustrating the structure of a liquid rocket engine according to another embodiment of the present invention.
  • Fig. 2 is a longitudinal sectional view showing the structure of the electric motor casing for cooling of the present invention.
  • FIG. 3 is a view showing a cooling unit of the present invention having a structure different from that of FIG.
  • 4 and 5 are structural diagrams showing the structure of a conventional liquid rocket engine.
  • One aspect of the present invention is a main combustion unit for supplying and burning an oxidant and fuel, a main oxidant line for guiding the oxidant contained in an oxidant tank to the main combustion unit, and guiding the fuel contained in a fuel tank to the main combustion unit.
  • a fuel booster pump installed in the main fuel line between a tank and the fuel pump, an electric motor disposed between the oxidant booster pump and the fuel booster pump and driven to drive the oxidant booster pump and the fuel booster pump;
  • a gas generator for generating a gas of high temperature and high pressure
  • an auxiliary oxidant line branched between the main combustion unit and the oxidant pump to guide a part of the oxidant to the gas generator, and branched between the main combustion unit and the fuel pump
  • a turbine for rotating a portion of the fuel to the gas generator, the auxiliary fuel line and the high temperature and high pressure gas generated in the gas generator, and driving the oxidant pump and the fuel pump.
  • one end of the cooling line may be branched between the oxidant pump and the oxidant booster pump, and the other end may be connected between the oxidant booster pump and the oxidant tank.
  • one end of the cooling line may be branched between the fuel pump and the fuel booster pump, and the other end may be connected between the fuel booster pump and the fuel tank.
  • one end of the cooling line is connected to the oxidant pump and the other end is exposed to the outside, so that the oxidant leaking from the oxidant pump may exchange heat with the electric motor and be discharged to the outside.
  • one end of the cooling line may be branched between the main combustion chamber and the oxidant pump, and the other end may be connected between the oxidant tank and the oxidant pump.
  • one end of the cooling line may be branched between the main combustion engine and the fuel pump, and the other end may be connected between the fuel tank and the fuel pump.
  • the cooling unit may have a cylindrical shape for accommodating the electric motor, and a flow path may be disposed therein.
  • the cooling unit may be wound around the outer circumferential surface of the electric motor to have a coil shape, and may be connected to one end of the cooling line and the other end of the cooling line.
  • the electric motor may coaxially connect the oxidant booster pump and the fuel booster pump.
  • the electric motor may be provided in a pair connected to the oxidant booster pump and the fuel booster pump, respectively.
  • the apparatus may further include a battery connected to one side of the cooling line and supplying power to the electric motor, wherein the cooling line guides the oxidant or fuel to the battery, and the cooling unit may be installed in the battery. .
  • the battery may further include an igniter connected to the battery and installed at one side of the main combustion device to ignite the main combustion device with an electric spark.
  • At least one of the oxidant and the fuel may be condensed in the condenser after passing through the cooling unit.
  • FIGS. 1A and 1B are conceptual views illustrating a structure of a liquid rocket engine using a booster pump driven by an electric motor according to an embodiment of the present invention and modified examples thereof, and FIGS. 1C to 1E illustrate another embodiment of the present invention. It is a conceptual diagram which shows the structure of the liquid rocket engine which concerns on an example, and FIG. 2 is a longitudinal cross-sectional view which shows the structure of the electric motor casing for cooling of this invention.
  • the liquid rocket engine 100 using the booster pump driven by the electric motor according to the present invention is provided with an oxidant booster pump and a fuel booster pump at the inlet side of the oxidant pump and the fuel pump, respectively. It is configured to operate in low pressure conditions in oxidant tank and fuel tank.
  • the electric motor can be cooled by adding a cooling line and a cooling unit.
  • the liquid rocket engine 100 using the booster pump driven by the electric motor according to the present invention includes a main combustion unit 101 for burning and receiving an oxidant and fuel, and the oxidant contained in the oxidant tank to the main combustion unit ( A main oxidant line 110 leading to 101, a main fuel line 120 guiding the fuel contained in a fuel tank to the main combustion engine, and a main oxidant line 110 and a main fuel line 120, respectively.
  • the oxidant booster pump 140 and the fuel booster pump 145 which are electrically driven may have a significantly lower inlet pressure than the inlet pressure required by the oxidant pump 130 and the fuel pump 135 driven by the turbine 195. Because of this, the internal pressure of the oxidant tank and fuel tank can be lowered and the tank thickness can be made relatively thin to reduce the weight of the projectile.
  • a gas generator 190 for generating a gas of high temperature and high pressure, an auxiliary oxidant line 117 for guiding a part of an oxidant to the gas generator 190, and an auxiliary fuel line for guiding a part of fuel to the gas generator 190.
  • the turbine 195 is rotated by the high temperature and high pressure gas of the gas generator 190 to drive the oxidant pump 130 and the fuel pump 135.
  • main oxidant on-off valve 115 for turning on and off the oxidant guided to the main combustor 101
  • main fuel on-off valve 121 gas generator 190 for turning on and off the fuel guided to the main combustor 101
  • An auxiliary oxidant on / off valve 118 for turning on and off the oxidant guided to the secondary fuel outlet valve 128 for turning on and off the fuel guided to the gas generator 190 is installed.
  • the oxidant booster pump 140, the fuel booster pump 145 and the oxidant pump 130, the fuel pump 135 In this case, all the pumps are driven simultaneously or the oxidant booster pump 140 and the fuel booster pump 145 are driven first.
  • auxiliary oxidant valve 118 and the auxiliary fuel valve 128 are opened to supply oxidant and fuel to the gas generator, and the supplied propellant (oxidant and fuel) is burned in the gas generator so that combustion gas of high temperature and high pressure is generated.
  • the turbine is driven again to rotate the oxidant pump 130 and the fuel pump 135.
  • the electric motor 150 for driving the oxidant booster pump 140 and the fuel booster pump 145 is continuously overheated while being overheated.
  • the cooling line 170 described above for cooling the overheated electric motor 150 is performed.
  • a cooling part is comprised.
  • the cooling line 170 is connected to one side of the main oxidant line 110 to guide a part of the oxidant to the electric motor 150, a supply unit 171 for supplying the oxidant to the cooling unit, and the cooling
  • the discharge unit 175 may be configured to guide the oxidant discharged from the unit.
  • the supply unit 171 may be configured to provide a cooling line open / close valve 173 to supply the oxidant only when the electric motor 150 is overheated, or may be configured to always cool by omitting the open / close valve. .
  • the cooling unit cools the electric motor 150 by the oxidant supplied through the cooling line 170, and as shown in FIG. 2, the tubular cooling for accommodating the electric motor 150.
  • Motor casing 180 may be exemplified, but may be configured to include a flow path (not shown) inside the casing.
  • the main oxidant line 110 is a booster pump inlet side oxidant line 111 connected to the oxidant tank based on the oxidant booster pump 140 and a booster pump outlet connected to the oxidant pump 130.
  • the side oxidant line portion 113 is formed.
  • the supply part 171 is connected to the booster pump outlet side oxidant line part 113, and the discharge part 175 is preferably connected to the booster pump inlet side oxidant line part 111.
  • the oxidant may be liquefied oxygen, which is present as a liquid in the main oxidant line 110, but diffuses into the cooling electric motor casing 180 at the supply unit and is heated by contact with the electric motor 150. It vaporizes.
  • the vaporized oxidant cools the electric motor 150 while undergoing a process of flowing into the booster pump inlet side oxidant line part 111 while being liquefied again through the condenser 177 installed in the discharge part 175. .
  • the electric motor may be a pair of single-axis electric motors connected to the oxidant booster pump 140 and the fuel booster pump 145, respectively, as shown in FIG. 1A, and as shown in FIG. 1B.
  • the oxidant booster pump 140 and the fuel booster pump 145 may be illustrated as one biaxial electric motor connecting coaxially.
  • the liquid rocket engine system can be driven without loss of the oxidant.
  • An igniter 102 may be installed at one side of the main combustion device 101 to ignite the main combustion device 101.
  • the igniter 102 may be driven in an electric spark manner and may receive a driving source from the battery 151.
  • the battery 151 transmits a driving force to the electric motor 150, and may be spaced apart from or adjacent to the electric motor 150.
  • the conventional ignition system there is a limit on the number of engine ignitions. If the engine needs to be restarted, the number of times required is a cartridge.
  • the teal cartridge is in the form of aluminum powder, there is a possibility of explosion in handling, and additional control valves must be installed to control the teal cartridge.
  • the liquid rocket engine 100 since the liquid rocket engine 100 according to the embodiment of the present invention ignites the engine by using an electric spark, stability may be improved.
  • the igniter 102 since the igniter 102 may receive energy from the battery 151 driving the electric motor 150, the igniter 102 may reduce the volume and weight of the system.
  • the energy source can be continuously transmitted from the battery 151, the engine can be re-ignited without installing an additional cartridge.
  • the second embodiment of the present invention is different in that it uses a fuel other than an oxidant as a refrigerant for cooling the electric motor.
  • the cooling line includes a supply unit 171 for supplying the fuel to the cooling unit, for example, the electric motor casing 180 for cooling, and a discharge unit 175 for guiding the fuel discharged from the cooling unit. .
  • the main fuel line 120 includes a booster pump inlet side fuel line part 124 connected to the oxidant tank based on the fuel booster pump 145, and a booster pump outlet side connected to the fuel pump 135. It consists of a fuel line part 125.
  • the supply part 171 is connected to the booster pump outlet side fuel line part 125, and the discharge part 175 is connected to the booster pump inlet side fuel line part 124.
  • the oxidant is used as a coolant for cooling the electric motor and the like as in the first embodiment described above, but does not bypass the oxidant as in the first embodiment.
  • the difference is that the oxidant used for cooling is discharged to the outside.
  • the supply unit 175 of the cooling line is connected to the oxidant pump 130 on one side and the other side is connected to the cooling unit, specifically the casing 180 to supply the oxidant to the casing 180, the discharge unit One side 170 is connected to the casing 180 and the other side is exposed to the outside to guide the oxidant to the outside.
  • the cooling line can be used not only for the electric motor 150, but also for cooling the battery 151.
  • the fourth embodiment of the present invention is the same in that the electric motor or the battery is cooled by bypassing the oxidant as in the first and second embodiments described above, but the supply unit 171 is the oxidant.
  • the pump 130 is connected to the main oxidant line portion 115 at the outlet side connected to the main combustion apparatus 101, and the difference is that the discharge portion 175 is connected to the outlet oxidant line portion 113. .
  • the discharge unit 175 may be configured to communicate with the inlet-side main fuel line unit 122 to bypass the fuel.
  • FIG. 3 is a view showing a cooling unit of the present invention having a structure different from that of FIG.
  • the cooling unit is wound around the outer circumferential surface of the electric motor 150, and one end thereof communicates with the supply unit 171, and the other end thereof communicates with the discharge unit 175. It consists of a coil-shaped cooling tube 185.
  • the cooling tube 185 has the same diameter as that of the supply unit 171 and the discharge unit 175, the liquid oxidant is circulated as a refrigerant without vaporization.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un moteur-fusée à propergol liquide s'appuyant sur une pompe de suralimentation entraînée par un moteur électrique et, plus particulièrement, un moteur-fusée à propergol liquide s'appuyant sur une pompe de suralimentation entraînée par un moteur électrique, le moteur-fusée à propergol liquide ayant une pompe de suralimentation entre un réservoir de propergol et une pompe de propergol de manière à satisfaire la pression d'entrée requise par le réservoir de propergol même dans un état dans lequel la pression interne du réservoir de propergol est abaissée, ce qui permet de réduire la quantité de propergol et le poids du réservoir de propergol, et refroidit efficacement le moteur électrique, qui entraîne la pompe de suralimentation, par l'intermédiaire d'un comburant, d'une ligne de refroidissement, et analogues.
PCT/KR2016/010319 2015-09-14 2016-09-13 Moteur-fusée à propergol liquide s'appuyant sur une pompe de suralimentation entraînée par un moteur électrique WO2017048041A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
KR1020187010421A KR102041568B1 (ko) 2015-09-14 2016-09-13 전기모터로 구동되는 부스터 펌프를 사용하는 액체로켓엔진
EP16846862.7A EP3318745B1 (fr) 2015-09-14 2016-09-13 Moteur-fusée à propergol liquide s'appuyant sur une pompe de suralimentation entraînée par un moteur électrique
US15/750,757 US11060482B2 (en) 2015-09-14 2016-09-13 Liquid rocket engine using booster pump driven by electric motor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR20150129674 2015-09-14
KR10-2015-0129674 2015-09-14

Publications (1)

Publication Number Publication Date
WO2017048041A1 true WO2017048041A1 (fr) 2017-03-23

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PCT/KR2016/010319 WO2017048041A1 (fr) 2015-09-14 2016-09-13 Moteur-fusée à propergol liquide s'appuyant sur une pompe de suralimentation entraînée par un moteur électrique

Country Status (4)

Country Link
US (1) US11060482B2 (fr)
EP (1) EP3318745B1 (fr)
KR (1) KR102041568B1 (fr)
WO (1) WO2017048041A1 (fr)

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EP3726027A1 (fr) * 2019-04-17 2020-10-21 United Technologies Corporation Système de gestion thermique intégré pour refroidissement de carburant
RU2729310C1 (ru) * 2019-08-04 2020-08-05 Андрей Владимирович Иванов Жидкостный ракетный двигатель
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KR102041568B1 (ko) 2019-11-06
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EP3318745B1 (fr) 2020-03-11
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